Spacecraft Line of Sight Maneuver Control Using Skew-arrayed Two Single-Gimbal Control Moment Gyros

• KOJIMA Hirohisa

  Department of Aerospace Engineerg, Tokyo Metropolitan University

• TRIVAILO Pavel

  School of Aeropace, Mechanical and Manufacturing Engineering, RMIT University

• YOSHIMURA Yasuhiro

  Department of Aerospace Engineerg, Tokyo Metropolitan University

Abstract

This paper considers line-of-sight (LOS) maneuver control of an underactuated spacecraft equipped with two skewed singlegimbal control moment gyros. To describe the spacecraft attitude, two parameters referred to as the W-Z parameters are used, the first of which represents the angle between the target LOS and the LOS of the mission-equipment, and the second of which represents the angle around the LOS. In order to stabilize the mission-equipment LOS to the target LOS, a two-step attitude control procedure is considered, which consists of feedforward control combined with feedback control based on a backstepping control method using the W-Z parameters. A numerical simulation is carried out to validate the proposed control procedure.

Journal

• TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN

  TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 14 (ists30), Pd_31-Pd_37, 2016

  THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Keywords

• <i>W</i>-<i>Z</i> Parameters
• Control Moment Gyro
• Line of Sight
• Attitude Maneuver

Details

• CRID: 1390001205319310208
• NII Article ID: 130005246074
• DOI: 10.2322/tastj.14.pd_31
• ISSN: 18840485
• Web Site: https://www.jstage.jst.go.jp/article/tastj/14/ists30/14_Pd_31/_pdf
• Text Lang: en
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
  • KAKEN
• Abstract License Flag: Disallowed